Data obtained at various frequencies and amplitudes for angles of attack from 0 to about 32° using oscillatory technique; static lateral and longitudinal stability data obtained at Mach number of 0.13 and Reynolds number of about 0.83×106.


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    Title :

    Effects of fuselage nose length and canopy on low-speed oscillatory yawing derivatives of swept-wing airplane model with fuselage of circular cross section


    Additional title:

    NASA -- Memo


    Contributors:


    Publication date :

    1959


    Size :

    28 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :